EP4194342A1 - Kryogener nichtkreisförmiger wasserstoffrückentank - Google Patents

Kryogener nichtkreisförmiger wasserstoffrückentank Download PDF

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Publication number
EP4194342A1
EP4194342A1 EP21213828.3A EP21213828A EP4194342A1 EP 4194342 A1 EP4194342 A1 EP 4194342A1 EP 21213828 A EP21213828 A EP 21213828A EP 4194342 A1 EP4194342 A1 EP 4194342A1
Authority
EP
European Patent Office
Prior art keywords
aircraft
tank
skin
stiffeners
fuselage
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
EP21213828.3A
Other languages
English (en)
French (fr)
Inventor
Claus-Peter Gross
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations GmbH
Original Assignee
Airbus Operations GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations GmbH filed Critical Airbus Operations GmbH
Priority to EP21213828.3A priority Critical patent/EP4194342A1/de
Priority to US18/075,308 priority patent/US20230184382A1/en
Priority to CN202211589415.8A priority patent/CN116255559A/zh
Publication of EP4194342A1 publication Critical patent/EP4194342A1/de
Pending legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C1/00—Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge
    • F17C1/02—Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge involving reinforcing arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C3/00—Vessels not under pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/02—Tanks
    • B64D37/04—Arrangement thereof in or on aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/30—Fuel systems for specific fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C1/00—Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge
    • F17C1/14—Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of aluminium; constructed of non-magnetic steel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C13/00—Details of vessels or of the filling or discharging of vessels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2201/00—Vessel construction, in particular geometry, arrangement or size
    • F17C2201/01—Shape
    • F17C2201/0147—Shape complex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2203/00—Vessel construction, in particular walls or details thereof
    • F17C2203/01—Reinforcing or suspension means
    • F17C2203/011—Reinforcing means
    • F17C2203/012—Reinforcing means on or in the wall, e.g. ribs
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2221/00—Handled fluid, in particular type of fluid
    • F17C2221/01—Pure fluids
    • F17C2221/012—Hydrogen
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2223/00—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel
    • F17C2223/01—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel characterised by the phase
    • F17C2223/0146—Two-phase
    • F17C2223/0153—Liquefied gas, e.g. LPG, GPL
    • F17C2223/0161—Liquefied gas, e.g. LPG, GPL cryogenic, e.g. LNG, GNL, PLNG
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2223/00—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel
    • F17C2223/03—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel characterised by the pressure level
    • F17C2223/033—Small pressure, e.g. for liquefied gas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2270/00—Applications
    • F17C2270/01—Applications for fluid transport or storage
    • F17C2270/0186—Applications for fluid transport or storage in the air or in space
    • F17C2270/0189—Planes

Definitions

  • the invention relates to an aircraft tank for a hydrogen-powered aircraft and to an aircraft provided with such an aircraft tank.
  • the object of the invention is to provide an aircraft tank providing more tank volume for storing cryogenic hydrogen.
  • the invention provides an aircraft tank according to claim 1.
  • Advantageous embodiments of the invention are subject-matters of the dependent claim.
  • the invention provides an aircraft equipped with such an aircraft tank
  • the invention provides an aircraft tank for storing cryogenic H2, wherein the aircraft tank is configured as non-circular dorsal tank.
  • the aircraft tank is configured as conformal fuel tank fitted to an outer contour of an aircraft fuselage.
  • At least one outer or inner skin segment of the tank has a cross section formed as a circular segment or elliptical segment.
  • first and second outer and/or inner skin segments are connected with a transition area having a stronger curvature compared to the curvature of the first and second skin segments.
  • a lower side of the tank to be arranged near to the aircraft fuselage has several skin segments connected by concave connection areas.
  • a lower side to be arranged near to an aircraft cabin has first to third skin segments with a convex curvature with concave connection areas therebetween.
  • the aircraft tank includes a series of reinforcement ribs connecting several skin segments of the tank in the interior of the tank.
  • the ribs have perforations enabling cryogenic H2 flow.
  • the ribs have several orifices for weight reduction.
  • the aircraft tank comprises an inner skin side reinforced with at least one of the reinforcement structures of the group consisting of flanges, stringers, orthogrid stiffeners, and isogrid stiffeners.
  • the aircraft tank comprises a flat or plate shaped bulkhead for closing a forward and/or backward end of the tank.
  • the aircraft tank comprises a closure bulkhead with at least one reinforcement structure.
  • the aircraft tank comprises a closure bulkhead reinforced with at least one of the reinforcement structures of the group consisting of longitudinal stiffeners, transversal stiffeners, orthogrid stiffeners, and isogrid stiffeners.
  • the aircraft tank comprises a bird-strike resistant forward closure bulkhead.
  • the aircraft tank comprises an inner skin defining an inner tank volume and an outer secondary skin enclosing the inner skin and defining an isolation chamber between the inner and outer skins.
  • a distance between the inner and outer skins is at least 40 mm.
  • the outer skin has an aerodynamic smooth outer surface and/or a fairing function.
  • the aircraft tank has an elongated tank body with a non-circular cross section.
  • a tank wall assembly of the tank body comprises at least one inner skin and at least one outer skin.
  • the invention provides an aircraft, especially passenger or cargo aircraft, comprising an aircraft tank according to any of the preceding embodiments.
  • the aircraft is a single-aisle or double aisle aircraft.
  • the aircraft has a fuselage containing a passenger cabin and/or a cargo space, wherein the non-circular H2 cryogenic dorsal tank is arranged on the top of the fuselage.
  • the aircraft tank is configured as conformal tank of the aircraft.
  • the outer skin of the aircraft tank has aerodynamical smooth transitions to the outer skin of the fuselage.
  • cryogenic H2 tanks are normally cylindrical tanks or spherical tanks with a circular cross section. This has advantages with regard to a small surface enclosing a large volume, and correspondingly low weight of the tank, better thermal isolation and better handling of higher pressures within the tank.
  • the aircraft is a turbofan hydrogen-powered aircraft. Due to the powering with hydrogen, the aircraft produces zero CO2 emissions and can substantially reduce air pollutants such as nitrogen oxide, as well as helping prevent contrail formation. However, a larger tank volume is needed for storing H2 compared with kerosene.
  • embodiments of the invention provide, as (additional) tank position option, the dorsal tank configuration.
  • preferred embodiments of the invention propose a non-circular tank; especially, a non-circular tank which follows the shape of the fuselage.
  • One target of some embodiments is to make best use of the available cross-sectional area between dorsal tank and fuselage, avoiding unused space.
  • Preferred embodiments of the invention propose a non-circular cryogenic H2 aircraft dorsal tank.
  • the tank follows the shape of the fuselage and reduces the fairing wetted area.
  • Most preferred embodiments aim to make best use of the available cross-sectional area between dorsal tank and fuselage, avoiding unused space.
  • Preferred embodiments provide a dorsal tank arrangement comprising several non-circular H2 tanks.
  • the H2 tank or all H2 tanks are filled with liquid hydrogen and dimensioned for a maximum pressure of 5 bar.
  • the selected tank material is light metal such as an aluminium alloy, especially aluminium AL 2219.
  • Composites may be an option.
  • some of the areas of the tank wall or of skin segments thereof may be made from metal while other areas may be made form composite material.
  • skins of the tank can be made, at least partially from fibre reinforced plastics such as CFRP.
  • vacuum is assumed in between tank skin and outer aerodynamic tank skin for best isolation.
  • the temperature inside tank is ⁇ 20.27 K (-252.88°C).
  • Preferred embodiments provide a non-circular dorsal tank.
  • the tank follows outer contour of the fuselage.
  • the tank has circular outer skin segments.
  • the tank has ribs inside.
  • the tank has perforated ribs inside to enable cryogenic H2 flow.
  • the tank has ribs including weight reduction orifices.
  • the tank inner skin side is reinforced with flanges/stringers, orthogrid or isogrid stiffeners.
  • the tank has a flat reinforced closure bulkhead, especially reinforced e.g. by longitudinal, orthogrid or isogrid stiffeners.
  • the tank has a bird-strike resistant forward closure bulkhead.
  • the tank has a secondary outer skin with a distance of 40mm from tank skin providing an isolation chamber.
  • the tank has a secondary outer skin with a distance of minimum 40mm from tank skin providing the aerodynamic smoothness (no need of a fairing around the tank).
  • FIG. 1 and 3 show cross sections through a fuselage 10 of an aircraft 12 according to a first and second embodiment of the invention, while Fig. 2 shows a similar cross section through the aircraft 12a according to a first comparative example.
  • Fig. 4 and 7 show different views of a further aircraft 12b according to a second comparative example, while Fig. 5 and 8 show similar views of the aircraft 12a according to the first comparative example, and Fig. 6 and 9 show similar views of the aircraft 12 according to the first embodiment of the invention, a cross section thereof is also shown in Fig. 1 .
  • Fig. 4 and 7 show a conventional aircraft 12b (second comparative example) with turbofans 14 as engines powered by kerosine.
  • the kerosine is stored in aircraft tanks within the wings.
  • Fig. 2 , 5 and 8 show an aircraft 12a according to the first comparative example having turbofans 14 as engines which are powered by hydrogen.
  • the aircraft 12a according to the first comparative example comprises a dorsal tank arrangement 16a including several cylindrical aircraft tanks 18a which are configured to store cryogenic hydrogen.
  • These cylindrical hydrogen aircraft tanks 18a according to the first comparative example are also referred to as reference tanks in the following.
  • the aircraft 12a according to the first comparative example has, as visible in Fig. 2 , a fairing 20 with a supporting substructure for the cylindrical aircraft tank 18a. Hence, a large unused space 22 is present.
  • the aircraft 12 according to the first and second embodiments of the invention as shown in Fig. 1, 3 , 6 and 9 have a dorsal tank arrangement 16 with several aircraft tanks 18 according to a first and second embodiment of the invention.
  • the dorsal tank arrangement 16 includes a forward first aircraft tank 18-1 and a rear second aircraft tank 18-2.
  • the aircraft tanks 18, 18-1, 18-2 are configured to store cryogenic hydrogen and have an elongated tank body with non-circular cross section as shown in larger detail in Fig. 1 and 3 . Especially, the aircraft tanks 18, 18-1, 18-2 are configured as non-circular dorsal tanks. As visible from Fig. 1 and 3 , the aircraft tanks 18, 18-1, 18-2 are conformal fuel tanks fitted to an outer contour of the fuselage 10.
  • the aircraft tank 18 has a lower side 24 with a recess 26 which receives the top of the fuselage 10.
  • the lower side 24 comprises first to third (lower) skin segments 28-1, 28-2, 28-3 that are curved outwardly - convex curvature - connected by concavely curved connection areas 30 there between.
  • the upper part of the inner skin 32 of the aircraft tank 18 may be circular or elliptical in cross section as shown in Fig. 3 or may comprise several convexly curved (upper) skin segments 34-1, 34-2, 34-3.
  • the curvature of this fourth to sixth skin segments 34-1, 34-2, 34-3 may be circular or elliptical, as shown in Fig. 1 .
  • Transitions areas 36 between the upper skin segments 34-1, 34-2, 34-3 have a stronger curvature compared to the curvature of the upper skin segments 34-1, 34-2, 34-3.
  • the non-circular cryogenic H2 aircraft tank 18 makes best use of the cross-sectional area avoiding large fairings 20 and an unused space 22.
  • the wetted area of the aircraft tank 18 according to the embodiments of the inventions is significantly reduced compared to the reference tank 18a of the aircraft 12a of the first comparative example.
  • the non-cylindrical aircraft tank 18 has a reduced wetted area with improved aerodynamics and reduced fairing weight.
  • Fig. 10 to Fig. 14 show details of the structural concept of the inner skin 32 of the aircraft tank 18.
  • the inner skin 32 defines a tank volume 33 in its interior.
  • the inner skin 32 is a reinforced tank skin.
  • the inner skin 32 is reinforced by longitudinal stiffeners 38.
  • all skin segments 28-1, 28-2, 28-3, 34-1, 34-2, 34-3 comprise the longitudinal stiffeners 38 in the interior thereof (especially at the inner side of the inner skin 32).
  • the skin segments 28-2, 28-3, 34-1, 34-2, 34-3 could also be reinforced by orthogrid or isogrid structures (not shown).
  • closure bulkheads 40 the forward and rear ends of the aircraft tank 18 are closed by closure bulkheads 40; an example thereof is also shown in Fig. 13 .
  • the closure bulkhead 40 can be a flat, plate-like structure with reinforcements.
  • the bulkhead 40 has an orthogrid structure 42 for reinforcement.
  • the closure bulkhead 40 closes the tank 18, wherein stresses at the orthogrid structure 42 are below the allowable material stress.
  • the forward closure bulkhead 40 is reinforced in such way that it is resistant against bird strikes.
  • the interior of the aircraft tank 18 is provided with a series of reinforcement ribs 44.
  • the ribs 44 connect the skin segments 28-1, 28-2, 28-3, 34-1, 34-2, 34-3 to each other.
  • the ribs 44 are preferably plate-shaped structures.
  • the ribs 44 inside have mainly the functions to keep the outer shape and minimise deformation and keep the skin stress below the allowable material stress.
  • the ribs 44 are evenly distributed over the longitudinal direction within the interior of the aircraft tank 18.
  • the ribs 44 have orifices 46 at lowest points to enable a flow of (liquid) hydrogen.
  • the ribs 44 have several larger openings 48 in order to reduce their weight. For example, a number of three to fourty ribs 44 are provided within the interior tank.
  • the distance between the ribs 44 is less than one meter.
  • the aircraft tank 18 further comprises an outer skin 50.
  • the outer skin 50 of the aircraft tank 18 has an aerodynamic function.
  • the outer surface of the outer skin 50 is provided with aerodynamic smoothness, further, the outer skin 50 provides smooth transitions to the fuselage 10.
  • an isolation chamber 52 is established between the outer skin 50 and the inner skin 32.
  • the outer skin 50 has the further function of tank isolation.
  • the gap between the skins 32, 50 is selected such that a good isolation is possible.
  • the gap is at least 40 mm.
  • the isolation chamber 52 is evacuated and/or contains isolation material as this is generally known for cryogenic H2 tanks.
  • the aircraft tanks 18 according to the embodiments of the invention have been modelled in a finite element analysis to get a weight estimate and to estimate the stresses on the tank walls during use as liquid hydrogen tanks. The outcome was that the weight penalty of choosing a non-circular tank is compensated by the reduced fairing weight when compared with the first comparative example.
  • the aircraft tanks 18 according to the embodiments of the invention provide overall a smaller weight compared to the comparative example with the cylindrical aircraft tank 18a. Further, the material stresses at the skins 32, 50 and the ribs 44 are much smaller as the allowable material stress.
  • the aircraft 12 is preferably a passenger aircraft wherein the fuselage 10 contains a passenger cabin 54 and a cargo space 56. Further embodiments using a similar fuselage 10 are configured as cargo aircrafts. Especially, the aircraft 12 is a narrow-body aircraft or a wide-body aircraft.
  • the invention proposes an aircraft tank (18) for storing cryogenic H2 which is configured as a non-circular dorsal tank.
  • the aircraft tank (18) is configured as a conformal fuel tank fitted to an outer contour of an aircraft fuselage (10). Further, an aircraft 12 provided with such aircraft tank 18 has been described.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
EP21213828.3A 2021-12-10 2021-12-10 Kryogener nichtkreisförmiger wasserstoffrückentank Pending EP4194342A1 (de)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP21213828.3A EP4194342A1 (de) 2021-12-10 2021-12-10 Kryogener nichtkreisförmiger wasserstoffrückentank
US18/075,308 US20230184382A1 (en) 2021-12-10 2022-12-05 Hydrogen cryogenic non circular dorsal tank
CN202211589415.8A CN116255559A (zh) 2021-12-10 2022-12-12 用于储存低温h2的飞行器罐和包括该飞行器罐的飞行器

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP21213828.3A EP4194342A1 (de) 2021-12-10 2021-12-10 Kryogener nichtkreisförmiger wasserstoffrückentank

Publications (1)

Publication Number Publication Date
EP4194342A1 true EP4194342A1 (de) 2023-06-14

Family

ID=78829468

Family Applications (1)

Application Number Title Priority Date Filing Date
EP21213828.3A Pending EP4194342A1 (de) 2021-12-10 2021-12-10 Kryogener nichtkreisförmiger wasserstoffrückentank

Country Status (3)

Country Link
US (1) US20230184382A1 (de)
EP (1) EP4194342A1 (de)
CN (1) CN116255559A (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB202100665D0 (en) * 2021-01-19 2021-03-03 Rolls Royce Plc Aircraft with hydrogen storage tanks

Citations (5)

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US20050230554A1 (en) * 2004-03-30 2005-10-20 Airbus Deutschland Gmbh Reservoir for cryogenic fuels and vehicles
DE102014107316A1 (de) * 2014-05-23 2015-11-26 Airbus Operations Gmbh Tanksystem zur kryogenen Lagerung von Wasserstoff und Flugzeug mit einem Tanksystem zur kryogenen Lagerung von Wasserstoff
RU2614443C1 (ru) * 2015-10-15 2017-03-28 Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") Магистральный пассажирский самолет на криогенном топливе
GB2591255A (en) * 2020-01-22 2021-07-28 Airbus Operations Ltd An aircraft
GB2591253A (en) * 2020-01-22 2021-07-28 Airbus Operations Ltd An aircraft fuselage

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US3979005A (en) * 1974-05-13 1976-09-07 The Boeing Company Cryogenic tank and aircraft structural interface
GB1503510A (en) * 1974-12-19 1978-03-15 British Aircraft Corp Ltd Aircraft fuel storage means
US4611724A (en) * 1985-08-16 1986-09-16 Jbf Scientific Company, Inc. Fluid-storage tank
US4913380A (en) * 1988-10-13 1990-04-03 Omac, Inc. Fuel system for Canard aircraft
US5782427A (en) * 1994-11-28 1998-07-21 Hermach; Carl J. Tandem-engine aircraft propulsion module
US5845879A (en) * 1995-12-28 1998-12-08 Lockheed Martin Corporation Inflatable conformable fuel tank
US5779092A (en) * 1996-10-01 1998-07-14 Mega Corporation Baffle system for tank
US5975466A (en) * 1998-06-02 1999-11-02 Northrop Grumman Corporation Variable displacement fuel tank for aircraft
DE10008985A1 (de) * 2000-02-25 2001-08-30 Linde Ag Speicherbehälter
US8172181B2 (en) * 2006-12-22 2012-05-08 Calvin Burgess Fuel range for an aircraft
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Patent Citations (5)

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Publication number Priority date Publication date Assignee Title
US20050230554A1 (en) * 2004-03-30 2005-10-20 Airbus Deutschland Gmbh Reservoir for cryogenic fuels and vehicles
DE102014107316A1 (de) * 2014-05-23 2015-11-26 Airbus Operations Gmbh Tanksystem zur kryogenen Lagerung von Wasserstoff und Flugzeug mit einem Tanksystem zur kryogenen Lagerung von Wasserstoff
RU2614443C1 (ru) * 2015-10-15 2017-03-28 Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") Магистральный пассажирский самолет на криогенном топливе
GB2591255A (en) * 2020-01-22 2021-07-28 Airbus Operations Ltd An aircraft
GB2591253A (en) * 2020-01-22 2021-07-28 Airbus Operations Ltd An aircraft fuselage

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US20230184382A1 (en) 2023-06-15
CN116255559A (zh) 2023-06-13

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